Methods of forming flexible structures for a rocket motor assembly

Patent metadata

Field	Value
Publication number	US-10934973-B2
Application number	US-201816127076-A
Country	US
Kind code	B2
Filing date	Sep 10, 2018
Priority date	Feb 23, 2015
Publication date	Mar 2, 2021
Grant date	Mar 2, 2021

Abstract

A method of forming a flexible structure for a rocket motor assembly comprises forming a polysiloxane composition comprising at least two different silicone materials. A preliminary structure is formed from the polysiloxane composition. The preliminary structure is cured to crosslink at least a portion of different polysiloxane chains of the preliminary structure. A flexible structure for a rocket motor assembly, a flexible assembly for a rocket motor assembly, a moveable thrust nozzle assembly for a rocket motor assembly, and a rocket motor assembly are also described.

First claim

What is claimed is:

1. A method of forming a flexible annular seal for a rocket motor assembly from a polysiloxane composition comprising silicone materials, the method comprising:
selecting a first silicone material having a Shore A hardness within a range of from 13 to 17;
selecting a second silicone material having a Shore A hardness within a range of from 20 to 24;
combining the first silicone material and the second silicone material to form a homogenous polysiloxane composition including a uniform dispersion of the first silicone material and the second silicone material;
forming a preliminary structure having a annular shape from the homogenous polysiloxane composition; and
curing the preliminary structure to crosslink at least a portion of different polysiloxane chains of the preliminary structure and form the preliminary structure having a shear modulus less than about 26 psi.

2. The method of claim 1 , wherein selecting each of the first silicone material and the second silicone material to independently having the following chemical structure:

where each R independently comprises hydrogen, an aliphatic group, or a cyclic group;
each M independently comprises a vinyl group, a silanol group, an allyl group, a vinylcyclohexyl group, a styryl group, or a propargyl group; and
n comprises an integer from 2 to 10,000.

3. The method of claim 2 , wherein selecting each of the first silicone material and the second silicone material comprises selecting the first silicone material and the second silicone material to comprise different grades of same polysiloxane compound.

4. The method of claim 2 , wherein selecting each of the first silicone material and the second silicone material comprises:
selecting one of the first silicone material and the second silicone material to comprise a first polysiloxane compound; and
selecting other of the first silicone material and the second silicone material to comprise a second polysiloxane compound having a different functional group than the first polysiloxane compound.

5. The method of claim 2 , wherein selecting each of the first silicone material and the second silicone material to independently comprise a polysiloxane compound comprises independently selecting the first silicone material and the second silicone material to comprise a polysiloxane compound having a polymer backbone comprising repeating units of dimethylsiloxane, methylethylsiloxane, methylphenylsiloxane, diethylsiloxane, ethylphenylsiloxane, or diphenylsiloxane.

6. The method of claim 2 , wherein selecting each of the first silicone material and the second silicone material comprises independently selecting a polysiloxane compound of each of the at least two different silicone materials to comprise a vinyl-terminated polydimethylsiloxane.

7. The method of claim 2 , wherein the homogeneous polysiloxane composition further comprises at least one curing/crosslinking agent.

8. The method of claim 7 , wherein forming the homogeneous polysiloxane composition comprises selecting the curing/crosslinking agent to comprise one or more of dicumyl peroxide and bis-(2,4-dischlorobenzoyl)-peroxide.

9. The method of claim 8 , wherein forming the substantially homogeneous polysiloxane composition comprises forming the homogeneous polysiloxane composition to comprise from about 1.5 phr to about 2.5 phr of the curing/crosslinking agent.

10. The method of claim 2 , wherein forming the preliminary structure from the homogeneous polysiloxane composition comprises molding the homogeneous polysiloxane composition into the preliminary structure.

11. The method of claim 2 , wherein curing the preliminary structure to crosslink at least a portion of different polysiloxane chains of the preliminary structure comprises subjecting the preliminary structure to at least one of elevated temperatures and elevated pressures for a sufficient period of time to form a cured polysiloxane composition.

12. The method of claim 1 , wherein forming the homogeneous polysiloxane composition comprises substantially homogeneously dispersing the at least two different silicone materials throughout an entirety of the polysiloxane composition.

13. The method of claim 1 , wherein forming the homogeneous polysiloxane composition comprises: selecting the first silicone material to comprise a vinyl-terminated polydimethylsiloxane compound having a first molecular weight; and selecting the second silicone material to comprise another vinyl-terminated polydimethylsiloxane compound having a second molecular weight different than the first molecular weight.

14. The method of claim 1 , wherein forming the preliminary structure from the homogeneous polysiloxane composition comprises forming a bulk structure comprising the polysiloxane composition through one or more of injection molding, compression molding, transfer molding, and extrusion.

15. The method of claim 1 , wherein forming the preliminary structure from the homogeneous polysiloxane composition comprises forming a film comprising the polysiloxane composition over another structure through a solution casting process.

16. The method of claim 1 , wherein curing the preliminary structure comprises heating the preliminary structure at a temperature within a range of from about 50° C. to about 350° C. for a period of time within a range of from about 5 minutes to about 10 hours.

Assignees

• Northrop Grumman Innovation Systems Inc

Inventors

• Gajiwala Himansu M
• Hall Steven B

Classifications

• B32B7/022 Primary

  Mechanical properties · CPC title

• B32B2307/3065

  Flame resistant or retardant, fire resistant or retardant · CPC title

• B32B2307/306

  Resistant to heat · CPC title

• B32B2250/00

  Layers arrangement · CPC title

• B32B2605/18

  Aircraft · CPC title